JPS6120704B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an end portion of a jet propulsion engine, particularly installed in an aircraft, which has a fixed jet pipe and a nozzle pipe rotatably provided on the fixed jet pipe.

[Conventional technology]

An end jet propulsion engine of the above type is known from US Pat. No. 3,438,581. There, a cardan joint is used to pivot the propulsion nozzle pipe or the propulsion nozzle in any direction around a fixed pivot point. This is located inside the fixed pipe and propellant nozzle, and has the following disadvantages: That is, the cardan joint is exposed to hot gas. This is particularly disadvantageous in the case of afterburning operation. The cardan joint bearings are likewise present inside the stationary pipe and the propulsion nozzle. This also causes bearing problems due to hot gases. Furthermore, the gas flow is restricted by cardan joints and shoring. Moreover, the very large forces occurring in the propulsion nozzle are transmitted through the strut to the Cardan center point and to the outside through another strut.
This strut adds to the weight of the structure.

[Problem that the invention seeks to solve]

The problem that the present invention seeks to solve is to eliminate the Cardan joints and force-conducting parts located in the hot gas flow, to eliminate the aforementioned drawbacks, and, above all, to reduce the structural weight and space required for force-conducting. It is an object of the present invention to provide a device that allows a propulsion nozzle pipe to be pivoted in any direction around a substantially fixed pivot point with fewer turns.

[Means for solving the problem] The above problem can be solved by fixing the fixed jet pipe and the nozzle pipe to each other in the radial direction via a pin inserted into a vertical slit, and by attaching a hinge type to the outside of both pipes. The problem is solved by axially fixing the two pipes to each other via a coupled actuator, which actuator can be adjusted longitudinally for the pivoting of the nozzle pipe.

The end of the jet propulsion engine of the present invention has a fixed jet pipe and a nozzle pipe arranged on the fixed jet pipe so as to be able to turn in any direction. Each pipe of the nozzle pipe has a pair of pins at positions opposite to each other in the diametrical direction, and the pair of pins of the fixed jet pipe and the pair of pins of the nozzle pipe are arranged 90 degrees apart from each other, and the fixed jet pipe Each of the nozzle pipes has a pair of vertical slits at diametrically opposite positions, and each of the pins of each pipe has a pair of vertical slits provided in the opposite pipe of the pipe having the pin. The fixed jet pipe and the nozzle pipe are fixed to each other in the radial direction by being inserted into the pipe, and a pair of fixed jet pipes and a nozzle pipe are provided on the outside of each pipe at opposite positions in the diametrical direction and connected in a hinged manner. The actuators are fixed to each other in the axial direction by two pairs of actuators, and the two pairs of actuators are movable in the length direction about the pivot point of the nozzle pipe and parallel to the longitudinal centerline of the fixed jet pipe. , is configured so that the nozzle pipe can be rotated by its movement.

According to the invention, it is not only possible in principle to swivel the nozzle pipe in any direction about a practically constant swivel center point, but also to use a single large cardan joint both inside and outside. do not need. This will be explained in detail below.

Since there are no Cardan joints and force-conducting parts in the inner space of both the fixed jet pipe and the nozzle pipe through which the hot gas flows, the conventional disadvantages described above do not occur. A pin and a longitudinal slot generally parallel to the longitudinal centerline of the pipe, as a device fixed to the pipe or directly or indirectly connected to the pipe, which is also a grooved link guiding device, are provided in the inner space of both said pipes. not exist. Further, the actuator does not exist in the inner space of the pipe, but exists around the outer periphery of both pipes. Each actuator is hingedly connected to a respective pipe in a generally cardan-like or similar manner. The pins and vertical slits save weight and space. This also applies to actuators placed on the outside. The actuators extend generally parallel to the longitudinal centerline of the pipe, are elongated in the axial direction of the longitudinal centerline of the pipe, and, together with their hinge succession, project slightly radially around the outside of the pipe. Also, devices for changing the nozzle cross section are often provided in the vicinity of the actuator. Tail drag is relatively small.

Next, in the device of the present invention, when the longitudinal center line of the fixed jet pipe and the longitudinal center line of the nozzle pipe are on the same straight line, the straight line connecting the front hinge point and the rear hinge point of each of the two pairs of actuators is It runs parallel to the longitudinal centerline of the fixed jet pipe, and the rear hinge point and two pairs of pins on both pipes extend 360° around the pipe on a plane perpendicular to the longitudinal centerline of the fixed jet pipe. a plane perpendicular to the longitudinal centerline of another fixed jet pipe which is evenly distributed across and whose front hinge point is located forward of the plane perpendicular to the longitudinal centerline of said fixed jet pipe; It can be configured to be uniformly distributed over a 360° circumference of the pipe.

In the above device, the rear hinge points of the two pairs of actuators and the two pairs of pins of both pipes can be arranged on two planes that cut the fixed jet pipe in the longitudinal direction.

However, if there are space constraints or for other reasons, the position of the hinge point of the actuator may be shifted by the same angle in the same circumferential direction with respect to the position of the pin by 25° to 30°. can.

Also, in the above device, the four actuators are uniformly distributed over 360°.

Next, in the above device, the rear hinge points 27 of the two pairs of actuators substantially overlap the surfaces of both pipes on which the two pairs of pins are arranged, or are located further than the surfaces on which the two pairs of pins are arranged. It can be arranged in a plane perpendicular to the longitudinal centerline of the fixed jet pipe located somewhat rearward.

Further, when the longitudinal center line of the fixed jet pipe of the present invention and the longitudinal center line of the nozzle pipe are on the same straight line, the straight line connecting the front hinge points of each of the four actuators and their corresponding rear hinge points is fixed. The forward hinge points of a pair of actuators run parallel to the longitudinal centerline of the jet pipe and are diametrically opposed to each other, and the rear hinge points of a pair of actuators are diametrically opposed to each other of the remaining pipes, and both pipes. four pins having a fixed jet pipe are uniformly distributed over a 360° circumference of the pipe on a plane perpendicular to the longitudinal centerline of the fixed jet pipe, and the rear hinge point corresponding to the front hinge point is located at the center of the fixed jet pipe. They are uniformly distributed over a 360° circumference of the nozzle pipe on a plane perpendicular to the center line of the nozzle pipe behind the arranged position, and the front hinge point corresponding to the rear hinge point is on a plane perpendicular to the center line of the fixed jet pipe in front of the placed position.
It can be configured to be uniformly distributed over a 360° circumference of the pipe.

In the above device, the front hinge points of one pair of actuators diametrically opposed to each other among the four actuators and one pair of pins among the four pins of both pipes cut the nozzle pipe in the longitudinal direction. The rear hinge points of the pair of actuators and the remaining pair of pins can be placed on a plane that longitudinally cuts the fixed jet pipe and are diametrically opposed to each other in the remaining pipe.

In the above device, the four actuators are
It can be evenly distributed over 360°.

In the above device, the rear hinge points of one pair of actuators facing each other in the diametrical direction of the pipes among the four actuators and the rear hinge points of the pair of actuators facing each other in the diametrical direction of the remaining pipes are the same as those of the two pipes. It is arranged in a plane perpendicular to the longitudinal center line of the fixed jet pipe that substantially overlaps with the plane on which the pair of pins are arranged, or located somewhat rearward than the plane on which the two pairs of pins are arranged. be able to.

As described above, in the present invention, the pins and the vertical slits attached thereto are uniformly distributed over 360 degrees in one pipe and the other pipe, and are arranged alternately, and the two pairs of actuators are connected to each other in the pipe. They are arranged so as to face each other in the diametrical direction, with the opposing directions of each pair intersecting each other. The rear hinge point of the actuator is located on a surface that substantially overlaps the surface of both pipes on which the pin is arranged, or is located somewhat rearward of the surface on which the pin is arranged. Alternatively, only the rear hinge points of the pair of actuators are located in a plane that substantially overlaps the plane in which the pins are disposed, or is located somewhat further away from the plane in which the pins are disposed. In the latter case, where only the rear hinge points of a pair of actuators are arranged on the same plane as the plane on which the pin is arranged, or on a plane slightly behind it, a single point is set for each hinge point. It only requires one pivot axis and does not require any cardan joints.

Furthermore, even if the nozzle pipe has an extremely large turning angle, the center of turning does not move at all.

The device of the invention moves a pair of actuators diametrically opposed to each other in order to pivot a nozzle pipe about two mutually perpendicular axes running diametrically through a fixed jet pipe. It can be configured to be able to move in any direction. a pair of actuators and/or
or another pair of actuators are moved in mutually opposite directions, thereby pivoting the nozzle pipe about a transverse axis and/or a transverse axis perpendicular thereto, the position of the pivot point remaining substantially constant; Ru. The alternating arrangement of pins and (slits) in one pipe and the other prevents movement of the pivot point from the longitudinal axis of the fixed jet pipe.

Regarding actuators with special restraint connections,
a first actuator part in which each pair of actuators is hingedly connected to a nozzle pipe;
A device according to the invention can be used having a second actuator part hingedly connected to the fixed nozzle pipe, cooperating with an actuator part of the first actuator part.

In the device described above, a unit consisting of a hydraulic piston and a piston rod can be used as the first actuator part, while a hydraulic cylinder can be used as the second actuator part. In this case, a rack device is provided in the cylinder opposite to both piston rods, and a gear wheel meshing with the rack device is provided in the cylinder, and a flexible shaft is connected to the gear wheel. In this device, two diametrically opposed pistons are moved in opposite directions by receiving impacts in opposite directions. A locking connection or synchronization is then provided by means of a rack device and a flexible shaft.

Also, in the above-mentioned device, a pair of actuator parts can be applied, in which one actuator part consists of a threaded spindle and the other actuator part consists of a nut. In this case, miter gears are provided at the ends of the double threaded spindle, each miter gear is connected to one end of a flexible shaft, and the other end of the flexible shaft connected to both miter gears is Two meshing, synchronizing gear pairs and an adjustment motor are connected. The oppositely directed drives of the two threaded spindles are synchronized by a pair of gear wheels. The axial force is uniformly distributed through the actuator or the hinged connection of the actuator parts.
It is distributed over 360° and is led to four sections of the pipe or pipe reinforcing flange as described below.

In the present invention, the vertical slits and pins can be provided indirectly rather than directly on the pipe. That is, a plate-shaped plate that protrudes in the longitudinal direction from each of the fixed jet pipe and the nozzle pipe.
A substantially tangential carrier arm is fastened to the fixed jet pipe or cylindrical part of the nozzle pipe at three axially spaced points. The longitudinal slits and/or pins are then provided on the carrier arm. Due to the fact that the carrying arms are fixed to the pipes at three points, the introduction of force is uniformly distributed over the 360° circumference of both pipes. As a result, deformation of the pipe can be further reduced with less cost for reinforcing the pipe. This is also important for the packing effect between both pipes. Since the grooved link guide only transmits force laterally,
Only the plane part of the carrying arm is stressed. The carrying arm can then be designed as a light plate structure with a buckling support.

The carrying arms introduce lateral forces tangentially into the pipe reinforcement flange. In addition to the three-point retention of the carrier arm, this flange can also be used, in particular, for the hinged connection of the actuator or parts of the actuator. An actuating element, for example a spindle, can be hingedly connected to the carrier arm in order to change the nozzle cross section.

Thereby, the pivot point remains substantially constant and the nozzle pipe can be adjusted axially and the actuator or actuator parts can be adjusted longitudinally.

The end of the propulsion engine according to the invention in the case of a marine aircraft is in particular the end with an afterburner or an afterburner unit. It can be flanged to the basic engine as a preassembled assembly and consists of two subassemblies. Namely, the first subassembly is the front afterburner as a fixed pipe with a mounted heat shield, a protruding carrying arm, a swivel spindle, an adjustment motor, and a flexible shaft, and a heat mounted It consists of a second sub-assembly, which is a pivotable afterburner as said nozzle pipe, with a shield, a projecting carrying arm and a propulsion nozzle.
The assembly operation of both subassemblies is carried out by pushing one into the other axially, with the
The grooved link guide mates with the packing and heat shield described above.

Control of the propulsion nozzle pipe, also called propulsion vector control, is performed as follows. A swivel angle is previously imparted by the pilot, and due to the circumferential misalignment of the actuator and the pin, the movement of the position according to the embodiment described in paragraph 3 causes the actuator or the pair of actuator parts, e.g. the pair of spindles, to The target value of can be determined by computational logic. The setpoint value-actual value comparison takes place via the control signal of the regulating motor or air motor. The rotational speed of this motor is determined to enhance the stability of the control system and reduce overspeeding. The swing angle feed device is arranged in the longitudinal slit.
The turning angle is therefore measured directly and error-free. The actual values for the control of the above-mentioned pairs are given by transformations by further computational logic. It is also possible to measure the control of a spindle or the like using the adjustment motor or air motor itself and report back.

The pins may also be, for example, sliding block cranks or rollers. Typically, the vertical slits open at the front of the pipe and begin there. This also applies if there are vertical slits in the carrying arm. The longitudinal slit is at least long enough to be able to carry out a pivoting of the propulsion nozzle pipe up to the desired maximum pivot angle, and so that the pin is not adjacent to the root of the longitudinal slit. In the case of arrangements for cardan-like or similar grooved linkage devices, the well-known devices with single or multiple gimbal rings, the well-known ball joints (ball and shell surrounding the device), etc. , there must always be the possibility of turning in all directions around a point.

[Effect]

In the device of the invention, lateral forces are transmitted by the grooved link guide and axial forces are transmitted by the linear actuator. Separation of axial forces from lateral forces and distribution of axial forces to multiple force entry points is achieved. And thereby the deformation of the pipe even when subjected to higher loads is very small, the deformation being much smaller than in the case of known constructions with cardan joints. This also applies if the total weight of the swivel device is lower. Lateral forces are introduced tangentially into the pipes to be pivoted around each other and can be transmitted to the reinforcement with relatively little outlay. Uniform force distribution and favorable structural partial stresses result in an effective relationship between stiffness and weight. This and the advantages of the grooved link guide system result in a small installation volume.

The grooved link and linear actuator determine the pivot point or hinged center point. For all small turn angles from 0° to approximately 15° to 20°, and for all directions of turn (especially in all directions controlling a stalled aircraft), the longitudinal centerline of both pipes is substantially The positional relationship, i.e., the circumferential and axial directions of the pin, the longitudinal slit, and the hinge point of the actuator, so that they intersect at a single and identical point and the position of the pivot point does not change in the axial and radial directions of the pipe. Optimize your location or
Or it can be harmonized continuously.

Also, the pivoting motion can be performed substantially identical to the pivoting motion of a Cardan joint. Because of that,
The problem of sealing or packing between the two pipes or between the ends facing the hot gas outlet can be solved well. Generally, at the end of a jet propulsion engine, the rear end of the fixed pipe is inside the front end of the nozzle pipe. However, the opposite is also possible. There is generally a 360° radial spacing between the ends, since at least one of the ends usually has a coaxially flat spherical shell. The coaxial packing provides a well-functioning seal in all the nozzle pipe rotational conditions.

〔Example〕

An embodiment of the invention is schematically illustrated in the drawing.

FIGS. 1 to 3 show the first part of the end portion according to the present invention.
Fig. 1 is a side view as seen from the direction shown in Fig. 2, Fig. 2 is a sectional view taken along the - line arrow shown in Fig. 1, and Fig. 3 is a longitudinal center of the pipe shown in Fig. 1. FIG. 3 is an enlarged detail view from a direction parallel to the line;

FIG. 4 is a side view showing a second embodiment of the end portion according to the present invention, viewed from the same direction as the side view shown in the first figure.

FIG. 5 is a perspective view showing a third embodiment of the end portion according to the present invention.

FIG. 6 is a schematic diagram illustrating a pair of actuators and their associated control devices in a particular technology.

FIG. 7 is a schematic diagram showing a pair of actuators and an attached drive device according to another technique.

As shown in Figures 1 and 2, the ends of the present invention taper in a conical manner toward the fixed jet pipe 10 and the cylindrical portion 12 and the rear. Propulsion nozzle 1
It has a nozzle pipe 11 consisting of three parts. The nozzle pipe 11 is shown with its orientation changed. The longitudinal center line 22 of the fixed jet pipe 10 and the longitudinal center line 23 of the nozzle pipe 11 are located on the same straight line. The forward end of the nozzle pipe 11 surrounds the rear end of the fixed jet pipe 10 at a radial distance. The fixed jet pipe 10 and the nozzle pipe 11 have two pins 16 which are inserted into a vertical slit 17 provided in the nozzle pipe 11 and which are fixed to the fixed jet pipe 10 and face each other in opposite directions in the radial direction. fixed to each other in the radial direction by the pin 16 and two pins 18 inserted into vertical slits 19 provided in the fixed jet pipe 10, which are fixed to the nozzle pipe 11 in radially opposite directions, and , mutually axially by a number of actuators parallel to the longitudinal center line of the fixed jet pipe 10, uniformly distributed over 360° and connected cardanically hinged to both pipes 10, 11. Fixed. The pin 16 is located in a plane perpendicular to the longitudinal centerline 22 of the fixed jet pipe, and the pin 18, which is displaced by about 90° with respect to the pin 16, is perpendicular to the longitudinal centerline 23 of the nozzle pipe. located on a flat plane. These planes are a single plane, ie, a cross section cut along the - line. The longitudinal slits 17 or 19 are in each case parallel to the longitudinal center line 23 of the nozzle pipe.
or starting from the front edge 25 or 15 of the nozzle pipe 11 or the fixed jet pipe 10, running parallel to and perpendicular to the longitudinal center line 22 of the fixed jet pipe. Vertical slit 17
and 19 have the same length and have a length approximately equal to the spacing between the front edges 25 and 15.
The Cardan joint for actuator 20 is illustrated by the joint center point. The hinge points are illustrated by 26 and 27. Hinge point 26,2
7 and pins 16, 18 are arranged with their positions different from each other by an angle α=27.5°. The rear hinge point 27 lies in a plane perpendicular to the longitudinal centerline 23 of the nozzle pipe, which plane
6 and 18 (located at the rear by about 3 mm when the diameter of the cylindrical portion of the nozzle pipe 11 is 800 mm). In FIG. 1 these planes substantially coincide. The forward hinge point 26 lies in a plane 68 perpendicular to the longitudinal centerline 22 of the fixed jet pipe. The nozzle pipe 11 can pivot around a vertical horizontal axis 21 and a horizontal horizontal axis 24 perpendicular thereto. The two horizontal axes 2
1 and 24 are located on the cross section cut along the - line, and enter the center of rotation 14 of the nozzle pipe. Pivoting is accomplished by longitudinal movement of actuator parts of a pair of actuators 20 in opposing directions (eg, as shown in FIGS. 6 and 7). Note that the plane that cuts the pipe in the longitudinal direction is indicated by 60.

FIG. 3 shows the front cardan joint or hinge point 26 for the hinged connection, for example the spindle 49 (shown in FIG. 7). An outer ring 61 is supported pivotably about a radial axis 63 by means of radial pins 62 fixed to the fixed jet pipe 10, and an inner ring 64 is attached to the outer ring 61 and has an inner ring 64 perpendicular to said axis 63. , is rotatably supported by an insertion pin inserted into the outer ring 61 around a shaft 65 supported on the plane of the outer ring. The spindle 49 is rotatable within the inner ring 64 and is longitudinally fixed relative to the inner ring. In the case of the rear cardan joint or hinge point 27, there is no inner ring, the bayonet pin of the ring is located on the radial axis, and instead of the radial pin there are two chevrons, on which the single ring 61 The only one is pivotably supported around the other shaft 65.

Through its rear end, the nut 50 (FIG. 7) is pivotably journaled about a radial axis by means of a bayonet pin and is fixedly supported in the circumferential direction and longitudinally.

Figure 4 shows four actuators 7 parallel to the axis.
The front and rear hinge points 69 to 72 of 3,73;74,74 are connected to four pins 16,16;18,
18 and are arranged on the same longitudinal plane 60, 75, and the front hinge points 69, 69 of one actuator pair 73, 73 and the rear hinge points 72, 72 of the other actuator pair 74, 74. and pins 16, 16; 18, 18 are shown arranged in a plane 76 perpendicular to the longitudinal centerline of a single pipe. In that case, the pin 16 is fixed to the fixed jet pipe 10, and the pin 18 is fixed to the nozzle pipe 11 (this is the opposite of the cases shown in the first and second figures). A cardan joint with hinge points 69 and 72 is then attached to pin 16.
and 18.

FIG. 5 shows the carrying arm. 28 and 29 indicate supporting arms, and the front fixed afterburner pipe 3
0 and a cylindrical part of a pivotable afterburner pipe 31 at each of three points 32 to 34. They are vertical slits 17
, 19 and 35 are distributed as shown in the first and second figures and are arranged over 360 degrees with respect to each other so as to be offset. The cylinder reinforcing flange and the inner cylinder, which plays the role of supplying high-temperature gas, are omitted because they are single.

In the case of the actuator pair shown in FIG. 6, two hydraulic cylinders 36 and, from time to time, hydraulic pistons 3
7, a piston rod 38 and a rack device 39 located in the cylinder 36 opposite the piston rod. Associated with the rack device 39 is a gear wheel 41 which is arranged at the end of a flexible shaft 40. The inner spaces of the cylinders 36, which are separated from each other by the pistons, are cross-connected to each other through conduits 42 and 43, and a control device 44 directs pressure oil to the opposite sides of the piston 37 via conduits 45 and 46. side, so that both piston rods 38 are connected to the pipe 1
1 or 31 are moved in mutually opposite directions so as to pivot about both transverse axes 21 and 24.
The hinged connection in the fixed pipe 10 or 30 takes place via a hinged connection part 47 of the cylinder 36, and the hinged connection in the pivotable pipe 31 or 31 takes place via a hinged connection part 48 of the piston rod 38. It is done.

In the case of a pair of actuators as shown in Figure 7,
It has two spindles (threaded spindles) 49
and two nuts 50, two flexible shafts 51, a pair of synchronous gears 52, an adjusting motor 53, and a miter gear 54 arranged in different directions. The rear end of the nut 50 is hingedly connected to the rotatable afterburner pipe by a cardan joint or the like. Miter gear 54
is provided at the end of a spindle which is hingedly connected to the front fixed pipes 10, 30 by a cardan joint or the like. Shaft 51 connects the gear pair with miter gear 54 . The balancing shaft 55, which is particularly flexible, serves to compensate for rotational moments caused by axial forces. This compensation balances the adjusting motor 53, which is a swivel drive or a pneumatic motor for driving both actuators or spindles 49. The adjusting motor 53 then only acts on the displacement moment and the frictional moment. Movements in mutually opposing directions are indicated by arrows 56 to 59.

〔Effect of the invention〕

As described in detail above, according to the present invention, not only can the nozzle pipe be turned in any direction around a substantially constant turning center point, but also
It has the advantage of not requiring a single large cardan joint on either the inside or the outside of the pipe.

Since there are no cardan joints and force transmission parts in the inner space of the fixed jet pipe and nozzle pipe through which hot gas flows, the drawbacks of conventional devices in which the cardan joint is located inside the pipe are eliminated. It is. In addition, the transverse force is transmitted by pins and longitudinal slits fixed to the pipe or provided directly or indirectly in the pipe as a grooved link guide device, and by a linear actuator. By constructing the structure so that axial force is transmitted, separating the axial force from the lateral force, and distributing the axial force to multiple force introduction points, the pipe can receive large loads. Even when this happens, the deformation of the pipe is very small, much smaller than in known constructions with cardan joints. or,
By appropriately selecting the positional relationship between the grooved link device consisting of a pin and a vertical slit as described above and the linear actuator, that is, the circumferential and axial positions of the pin, the vertical slit, and the hinge point of the actuator, the 0° For all small turn angles, from about 15° to 20°, and for all directions of turn (especially in all directions for control of a stalled aircraft), the longitudinal centerlines of both pipes are substantially at the same point. It has the advantage that the intersection and the position of the pivot point do not change in either the axial direction or the radial direction of the pipe.

[Brief explanation of the drawing]

FIGS. 1 to 3 show the first part of the end portion according to the present invention.
Fig. 1 is a side view as seen from the direction shown in Fig. 2, Fig. 2 is a sectional view taken along the - line arrow shown in Fig. 1, and Fig. 3 is a longitudinal center of the pipe shown in Fig. 1. Enlarged detailed front view, viewed from the direction parallel to the line,
FIG. 4 is a side view showing a second embodiment of the end portion according to the present invention, seen from the same direction as the side view shown in the first drawing, and FIG. 5 is a perspective view showing a third embodiment of the end portion according to the present invention. figure,
FIG. 6 is a schematic diagram showing a pair of actuators of a specific technology and a control device attached thereto, and FIG. 7 is a schematic diagram showing a pair of actuators of another technology and a drive device attached thereto. 30, 31, 10, 11...pipe, 17, 1
9... Vertical slit, 16, 18... Pin, 20,
73, 74... Actuator, 22, 23...
Longitudinal centerline of the pipe, 26, 27, 69 to 72... Hinge point, -, 68, 76... Plane perpendicular to the longitudinal centerline of the pipe, 60, 75
...plane that cuts the pipe in the longitudinal direction, 21, 24
... mutually perpendicular axes, 36 ... cylinders, 37 ...
... Piston, 38 ... Piston rod, 49 ... Spindle, 50 ... Nut, 41, 52 ... Gear,
40, 51...Flexible shaft, 53...
Adjustment motor, 54... Miter gear, 28, 29...
...carrying arm.

Claims (1)

[Claims] 1. A fixed jet pipe 1 at the end of a jet propulsion engine installed in an aircraft, which has a fixed jet pipe and a nozzle pipe arranged on the fixed jet pipe so as to be able to turn in any direction.
0 and the nozzle pipe 11 have a pair of pins 16, 16, 18, 1 at diametrically opposite positions.
8 and a fixed jet pipe 10
A pair of pins 16, 16 and 1 of the nozzle pipe 11
The pair of pins 18, 18 are arranged 90 degrees apart from each other, and each of the fixed jet pipe 10 and the nozzle pipe 11 has a pair of vertical slits 17, 17, 19, 19 at diametrically opposed positions. , and both pipes 10 and 11 are formed by each of the pins 16, 16, 18, 18 of each pipe being inserted into a vertical slit provided in the pipe opposite to the pipe having the pin. , two pairs of actuators 20 are fixed to each other in the radial direction, and are hingedly connected to the outside of each of the fixed jet pipe 10 and the nozzle pipe 11 at positions opposite to each other in the diametrical direction. Being axially fixed to each other, the two pairs of actuators 20 can be longitudinally moved about the pivot point 14 of the nozzle pipe, parallel to the longitudinal centerline of the fixed jet pipe, and by their movement: An end of a jet propulsion engine, characterized in that it is configured to allow a nozzle pipe to pivot. 2. When the longitudinal center line of the fixed jet pipe 10 and the longitudinal center line of the nozzle pipe 11 are on the same straight line, the straight line connecting the front hinge point 26 and the rear hinge point 27 of the two pairs of actuators 20 is the same as that of the two pipes. The rear hinge point 27 and the pins 16, 16 of the fixed jet pipe 10 and the pins 18, 18 of the nozzle pipe 11 run parallel to the longitudinal center line of the nozzle pipe 11. Vertical plane - 360 above
360° of pipe circumference, and the forward hinge points 26 lie on a plane 68 perpendicular to the centerline of the fixed jet pipe 10 separate from said plane. An end portion of a jet propulsion engine according to claim 1, characterized in that the end portion is uniformly distributed throughout. 3. The rear hinge points 27 of the two pairs of actuators 20 and the pins 16, 16 of the fixed jet pipe,
and two planes 60 where the pins 18, 18 of the nozzle pipe cut the fixed jet pipe 10 in the longitudinal direction.
The rear hinge points 27 of the two pairs of actuators 20 are arranged on the fixed jet pipe 1.
0 or the pins 18, 18 of the nozzle pipe 11, the nozzle pipe 11 is arranged so as to be displaced by the same angle α in the same circumferential direction. An end portion of the jet propulsion engine according to item 2. 4. An end portion of a jet propulsion engine according to claim 3, wherein the four actuators 20 are arranged uniformly distributed over 360 degrees. 5 The rear hinge points 27 of the two pairs of actuators 20 are connected to the pins 16 of the fixed jet pipe 10,
16, and the surface on which the pins 18, 18 of the nozzle pipe 11 are arranged, or the surface on which the pins 16, 16 of the fixed jet pipe 10 and the pins 18, 18 of the nozzle pipe 11 are arranged, The end portion of a jet propulsion engine according to claim 2, wherein the end portion of the jet propulsion engine is disposed in a plane perpendicular to the longitudinal center line of the nozzle pipe 11 located at the rear. 6 When the longitudinal center line of the fixed jet pipe 10 and the longitudinal center line of the nozzle pipe 11 are on the same straight line, the four actuators 73, 7
3, 74, 74 forward hinge points 69, 69, 7
1, 71 and their corresponding rear hinge points 70,
The straight line connecting between 70, 72, 72 is both pipes 10,
11 and a pair of diametrically opposed actuators 73, 73 and a pair of diametrically opposed actuators 74 of the remaining pipes. , 74 and the pins 16, 16 of the fixed jet pipe 10 and the pins 18, 18 of the nozzle pipe 11 are connected to the nozzle pipe 11.
The rear hinge points 70, 70 corresponding to the front hinge points 69, 69 are uniformly distributed over a 360° circumference of the pipe on a plane perpendicular to the longitudinal centerline of the and front hinge points 71, 7 which are located on a plane perpendicular to the longitudinal center line of the nozzle pipe 11 rearward of the plane where the pin is located and correspond to the rear hinge points 72, 72.
1 is on a plane perpendicular to the longitudinal center line of the fixed jet pipe 10, which is forward of the plane where the rear hinge point and the pin are located. end of. 7 The four actuators 73, 73, 7
1 of 4,74 opposite to the diameter of the pipe
Front hinge point 6 of paired actuators 73, 73
9, 69 and the four pins 16, 16, 18, 1
A pair of diametrically opposed pins 8 of 8 are disposed on the plane that longitudinally cuts the nozzle pipe 11, and a rear hinge point 72 of a pair of diametrically opposed actuators 74, 74 of the remaining pipe. ,7
7. The end portion of a jet propulsion engine according to claim 6, wherein the remaining pair of pins 18, 18 are arranged on a plane that cuts the fixed jet pipe 10 in the longitudinal direction. 8 The four actuators 73, 73, 7
8. An end portion of a jet propulsion engine according to claim 7, characterized in that the portions 4, 74 are arranged uniformly distributed over 360°. 9 The four actuators 73, 73, 7
1 of 4,74 opposite to the diameter of the pipe
Front hinge point 6 of paired actuators 73, 73
9, 69 and the rear hinge points 72, 72 of a pair of diametrically opposed actuators 74, 74 of the remaining pipes are connected to the two pairs of pins 16, 16, 1
With respect to the longitudinal centerline of the fixed jet pipe 10 that substantially overlaps the plane on which the pins 8 and 18 are arranged, or is located somewhat rearward of the plane on which the two pairs of pins 16, 16, 18, and 18 are arranged. 7. An end portion of a jet propulsion engine according to claim 6, wherein the end portion is arranged in a vertical plane. 10 Two mutually perpendicular axes 21, 2 running in the diametrical direction of the fixed jet pipe 10
The patent is characterized in that a pair of actuators 20 facing each other in the diametrical direction of the pipe can be moved in opposite directions in order to rotate the nozzle pipe 11 around the nozzle pipe 11. Claim 4 or 5 or 8 or 9
The end of the jet propulsion engine described in Section 1. 11 a pair of diametrically opposed actuators are hingedly connected to the fixed nozzle pipe 10 cooperating with a first actuator part hingedly connected to the nozzle pipe 11; Claim 1 characterized in that it has a second actuator component.
An end portion of the jet propulsion engine described in item 0. 12 A unit consisting of a hydraulic piston 37 and a piston rod 38 forms a first actuator part coupled in pair with the nozzle pipe 11, and a hydraulic cylinder 36 forms a second actuator part coupled in pair with the fixed jet pipe. 12. An end portion of a jet propulsion engine according to claim 11, characterized in that it forms an end portion of a jet propulsion engine. 13. The end of a jet propulsion engine according to claim 11, characterized in that one pair of actuator parts is a threaded spindle 49 and the other pair of actuator parts is a nut 50. 14. Both hydraulic pistons 37 can be moved in mutually opposite directions by receiving impacts in mutually opposite directions, and the movement of both piston rods is coupled to the rack device 39 and its gear 41. 13. The end of a jet propulsion engine according to claim 12, characterized in that it is synchronized by a flexible shaft (40). 15. A flexible shaft 51, 51 guided towards a double threaded spindle or nut 50 for movement in opposite directions and driven via the shaft by an adjusting motor 53;
Claim 13, characterized in that it has a gear 52 which is engaged and serves as a synchronizer.
The end of the jet propulsion engine described in Section 1. 16 Two threaded spindles 49 or nuts 5
Two miter gears 5 between 0 and the adjustment motor 53
16. An end portion of a jet propulsion engine according to claim 15, characterized in that said miter gears are provided with said miter gears and said flexible shafts 51 and 51 are connected to said miter gears. 17 Two pairs of substantially tangential plate-shaped carrier arms 2 projecting longitudinally from each of the fixed jet pipes 10, 30 and the nozzle pipes 11, 31;
8, 28, 29, 29, each carrying arm carrying a fixed jet pipe 10, 30 or a nozzle pipe 1.
Three points 32, 3 with axial spacing at 1, 31
3, 34, and longitudinal slits and/or pins are provided in the carrying arm. The end of the jet propulsion engine described.